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S2/2006 Socata TB10 G-BNRA
During a touch and go landing, as power was applied a propeller blade detached. The resulting imbalance caused both the crankshaft to fracture (allowing the propeller to be released) and the engine to partly separate from the structure. Metallurgical examination indicated the presence of fatigue in the propeller hub. The location and nature of the fatigue was similar to that described in an existing Service Bulletin, however that document has not yet been classified as mandatory by the FAA. Three Safety Recommendations are made.
S2-2006 G-BNRA.pdf (302.50 kb)